US8221062B2 - Device and system for reducing secondary air flow in a gas turbine - Google Patents

Device and system for reducing secondary air flow in a gas turbine Download PDF

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Publication number
US8221062B2
US8221062B2 US12/353,305 US35330509A US8221062B2 US 8221062 B2 US8221062 B2 US 8221062B2 US 35330509 A US35330509 A US 35330509A US 8221062 B2 US8221062 B2 US 8221062B2
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Prior art keywords
sealing member
rotor disk
buckets
inter
turbine
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US12/353,305
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English (en)
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US20100178160A1 (en
Inventor
Gary Charles Liotta
Thomas Raymond Farrell
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GE Vernova Infrastructure Technology LLC
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General Electric Co
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Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FARRELL, THOMAS RAYMOND, LIOTTA, GARY CHARLES
Priority to US12/353,305 priority Critical patent/US8221062B2/en
Priority to JP2010003534A priority patent/JP5491874B2/ja
Priority to HUE10150525A priority patent/HUE051990T2/hu
Priority to EP10150525.3A priority patent/EP2208860B1/en
Priority to CN201010005139.7A priority patent/CN101845996B/zh
Publication of US20100178160A1 publication Critical patent/US20100178160A1/en
Publication of US8221062B2 publication Critical patent/US8221062B2/en
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Assigned to GE INFRASTRUCTURE TECHNOLOGY LLC reassignment GE INFRASTRUCTURE TECHNOLOGY LLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC COMPANY
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the subject matter disclosed herein relates to gas turbines and, more particularly, to inter-stage seals in gas turbines.
  • Turbine components are typically directly exposed to high temperature gases, and therefore require cooling to meet their useful life. For example, some of the compressor discharge air is diverted from the combustion process for cooling rotor components of the turbine.
  • Turbine buckets, blades and vanes typically include internal cooling channels therein which receive compressor discharge air or other cooling gases for cooling thereof during operation.
  • turbine rotor disks which support the buckets are subject to significant thermal loads and thus also need to be cooled to increase their lifetimes.
  • the main flow path of the turbine is designed to confine combustion gases as they flow through the turbine.
  • Turbine rotor structural components must be provided with cooling air independent of the main gas flow to prevent ingestion of the hot combustion gases therein during operation, and must be shielded from direct exposure to the hot flowpath gas.
  • Such confinement is accomplished by rotary seals positioned between the rotating turbine buckets to prevent ingestion or back flow of the hot air or gases into interior portions of the turbine rotor structure.
  • Such rotary seals are insufficient to completely protect the interior components, such as the rotor structure, rotor and rotor disks, requiring the additional use of purge flows of cooling air into and through the rotor cavity.
  • Such additional measures to protect the interior components increase the cost and complexity and hinder the performance of gas turbines.
  • a device for reducing secondary airflow in a gas turbine constructed in accordance with exemplary embodiments of the invention includes: an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk and a plurality of second turbine buckets attached to a second rotor disk, the first rotor disk and the second rotor disk being rotatable about a central axis.
  • the inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
  • exemplary embodiments of the invention include a gas turbine system including: a plurality of first turbine buckets attached to a first rotatable rotor disk; a plurality of second turbine buckets attached to a second rotatable rotor disk; a plurality of stationary radially extending turbine nozzles located axially between the first rotor disk and the second rotor disk; and a rotatable inter-stage sealing member attached to the first and second rotating disks, the rotatable sealing member configured to contact the plurality of first turbine buckets and the plurality of second turbine buckets to form a sealed flow path defined by the plurality of first and second buckets and at least one of the plurality of stationary nozzles and the sealing member.
  • FIG. 1 is a side view of a portion of a gas turbine including a sealing assembly in accordance with an exemplary embodiment of the invention.
  • FIG. 2 is a side view of another exemplary embodiment of the sealing assembly of FIG. 1 .
  • FIG. 1 a portion of a turbine section of a gas turbine constructed in accordance with an exemplary embodiment of the invention is indicated generally at 10 .
  • the turbine 10 includes alternating inter-stage nozzle stages 12 and turbine stages 14 , 16 .
  • An inter-stage sealing assembly 18 is disposed between the turbine stages 14 , 16 .
  • FIG. 1 shows a side cross-sectional view of a first turbine stage 14 , a second turbine stage 16 , and the nozzle stage 12 and sealing assembly 18 therebetween.
  • Each turbine stage 14 , 16 includes a rotor disk 20 that is attached to a rotor shaft (not shown) that causes the rotor disks 20 to rotate about a central axis.
  • a plurality of blades or buckets 22 are removably attached to an outer periphery of each rotor disk 20 .
  • the buckets 22 are attached by any suitable mechanism, such as an axially extending dovetail connection.
  • the buckets 22 each include a bucket platform 23 configured to attach to the corresponding rotor disk 20 .
  • an “axial” direction is a direction parallel to the central axis
  • a “radial” direction is a direction extending from the central axis and perpendicular to the central axis.
  • An “outer” location refers to a location in the radial direction that is farther away from the central axis than an “inner” location.
  • the nozzle stage 12 includes a plurality of nozzle vanes 24 that are connected to an outer casing assembly such as a turbine shell or an outer support ring attached thereto, and extend radially toward the central axis.
  • each of the nozzle vanes 24 are attached to an inner support ring, or segments forming a ring 26 having a diameter less than a diameter of the outer support ring, or segments forming a ring.
  • the inter-stage sealing assembly 18 is included to reduce or prevent heated gas or air from leaking into interior portions of the turbine 10 and away from the flow path defined by the buckets 22 and the nozzle stage 12 .
  • the sealing assembly includes a sealing member 28 that is attached in a fixed position relative to the rotating rotor disks 20 , and therefore rotates along with the rotor disks 20 .
  • the sealing member 28 is also disposed against a surface of the buckets 22 , such as against the bucket platforms 23 , to cause a sealing connection between the sealing member 28 and the buckets 22 .
  • the corresponding gas flow path is accordingly defined by the buckets 22 and the inner support ring 26 , with leakage of gas flow from the flow path being prevented by the sealing member 28 .
  • the sealing member 28 is cast or otherwise made from high temperature materials capable of withstanding elevated temperatures such as 1500° F.
  • high temperature materials capable of withstanding elevated temperatures such as 1500° F.
  • examples of such materials include nickel based superalloys such as those alloys used for flowpath components.
  • the sealing member 28 is attached to an inter-stage disk 30 that is attached in fixed position relative to the rotor disks 20 .
  • the inter-stage disk 30 is attached to the rotor disks by a bolt connection 31 or other suitable attachment to, for example, flanges 33 .
  • the attachment designs described herein are not limited. Any suitable attached mechanism may be used to attach the sealing member 28 in a fixed position relative to the rotor disks 20 .
  • the sealing member 28 is a continuous circumferential ring having an outer diameter less than an inner diameter of the nozzle inner support ring 26 and/or the nozzle vane 24 .
  • the sealing member 28 is segmented and is attached to the inter-stage disk 30 by a removable connection such as a circumferential dovetail connection 32 .
  • the sealing member 28 includes at least one extension 34 at each axial end of the sealing member 28 that contact at least one axially-extending protrusion 36 on each of the buckets 22 such as the bucket platforms 23 . This contact between the extensions 34 and the protrusions 36 provides the seal between the buckets 22 and the sealing member 28 . This contact can be metal-to-metal or contain a separate sealing feature between the extension 34 and the protrusion 36 .
  • the sealing member 28 is made from high temperature-resistant materials that can withstand the high temperature of the flow path.
  • the sealing member 28 can be segmented with sealing features between circumferential segments, such as spline seals.
  • the sealing member 28 is made from any of various materials such as metal castings, forgings, composite materials and ceramic materials.
  • cooling air or other cooling means are applied to the sealing member 28 to counteract the high temperatures in the flow path.
  • the sealing member 28 thus protects the lower temperature rotating structures such as the rotor and rotor disks 20 from the hot gas of the flowpath, allowing for greatly reduced or eliminated rotor cavity purge flow levels since any local flow path ingestion occurs only on high temperature capable materials.
  • a buffer cavity 40 is formed between the sealing member 28 and the inner support ring 26 . This cavity 40 is surrounded by the high temperature materials of the sealing member 28 , ring 26 and bucket platforms 23 .
  • FIG. 2 another embodiment of the turbine section 10 is shown, in which the inner support ring 26 is omitted and the sealing member 28 forms the flow path along with the buckets 22 .
  • the nozzle vanes 24 are individually attached to the turbine shell in a cantilever arrangement.
  • a controllable gap 42 is defined between the sealing member 28 and the nozzle 24 .
  • an exemplary method for reducing secondary airflow in a gas turbine includes disposing the rotor disks 20 in at least one of the compression section and the turbine section.
  • the turbine nozzle vanes 24 are disposed axially between the rotor disks 20 .
  • the sealing member 28 is attached at a fixed position relative to the rotor disks 20 , and disposed to contact the buckets 22 .
  • the combustion section is activated to cause rotation of the rotors 20 and direct an air flow through a conduit formed by the buckets 22 and at least one of the nozzle stages 12 and the sealing member 28 .
  • the sealing member 28 prevents or reduces leakage of the air flow from the conduit during operation of the turbine 10 .
  • any other suitable type of turbine may be used.
  • the systems and methods described herein may be used with a steam turbine or turbine including both gas and steam generation.
  • the devices, systems and methods described herein provide numerous advantages over prior art systems.
  • the devices, systems and methods provide the technical effect of increasing efficiency and performance of the turbine by reducing the number of components and by reducing or eliminating the need for cooling gas flows.
  • the need for disk rim cover plates to seal the connection between the rotor disks and the buckets may be eliminated.
  • the prevention of air flow leakage into interior cavities of the turbine reduces the level of cooling flow required, thus improving turbine efficiency and reducing cost.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/353,305 2009-01-14 2009-01-14 Device and system for reducing secondary air flow in a gas turbine Active 2030-12-22 US8221062B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/353,305 US8221062B2 (en) 2009-01-14 2009-01-14 Device and system for reducing secondary air flow in a gas turbine
JP2010003534A JP5491874B2 (ja) 2009-01-14 2010-01-12 ガスタービン中の２次空気流を低減する装置およびシステム
HUE10150525A HUE051990T2 (hu) 2009-01-14 2010-01-12 Fokozatok közötti tömítés gázturbinához és az ennek megfelelõ gázturbina
EP10150525.3A EP2208860B1 (en) 2009-01-14 2010-01-12 Interstage seal for a gas turbine and corresponding gas turbine
CN201010005139.7A CN101845996B (zh) 2009-01-14 2010-01-14 用于在燃气轮机中减少二次空气流的装置和系统

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/353,305 US8221062B2 (en) 2009-01-14 2009-01-14 Device and system for reducing secondary air flow in a gas turbine

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US20100178160A1 US20100178160A1 (en) 2010-07-15
US8221062B2 true US8221062B2 (en) 2012-07-17

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US12/353,305 Active 2030-12-22 US8221062B2 (en) 2009-01-14 2009-01-14 Device and system for reducing secondary air flow in a gas turbine

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US (1) US8221062B2 (enrdf_load_stackoverflow)
EP (1) EP2208860B1 (enrdf_load_stackoverflow)
JP (1) JP5491874B2 (enrdf_load_stackoverflow)
CN (1) CN101845996B (enrdf_load_stackoverflow)
HU (1) HUE051990T2 (enrdf_load_stackoverflow)

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US20120003079A1 (en) * 2010-07-02 2012-01-05 General Electric Company Apparatus and system for sealing a turbine rotor
US8864453B2 (en) 2012-01-20 2014-10-21 General Electric Company Near flow path seal for a turbomachine
US20140334929A1 (en) * 2013-05-13 2014-11-13 General Electric Company Compressor rotor heat shield
US20150110628A1 (en) * 2013-10-17 2015-04-23 Pratt & Whitney Canada Corp. Fastening system for rotor hubs
US20160186592A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
US9404376B2 (en) 2013-10-28 2016-08-02 General Electric Company Sealing component for reducing secondary airflow in a turbine system
US9605596B2 (en) 2013-03-08 2017-03-28 United Technologies Corporation Duct blocker seal assembly for a gas turbine engine
US9957895B2 (en) 2013-02-28 2018-05-01 United Technologies Corporation Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers
US10138751B2 (en) 2012-12-19 2018-11-27 United Technologies Corporation Segmented seal for a gas turbine engine
KR102127429B1 (ko) 2019-06-05 2020-06-26 두산중공업 주식회사 터빈 로터 디스크와 인터스테이지 디스크 사이의 실링 구조
US11305927B2 (en) 2014-04-04 2022-04-19 Polytex Fibers Llc Easy open plastic bags
US11339662B2 (en) * 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
US11459157B2 (en) 2012-02-13 2022-10-04 Polytex Fibers Llc Woven plastic bags with features that reduce leakage, breakage and infestations
US11472622B2 (en) 2014-04-04 2022-10-18 Polytex Fibers Llc Woven plastic bags with features that reduce leakage, breakage, and infestations
US11801987B2 (en) 2014-04-04 2023-10-31 Polytex Fibers Llc Woven plastic bags with angled and/or radial cuts
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FR3009336B1 (fr) * 2013-08-05 2015-09-04 Snecma Ensemble rotatif de turbomachine muni d'une virole labyrinthe cmc
CN103541776B (zh) * 2013-10-15 2015-12-30 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机轮盘间的轴向密封结构
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FR3021692B1 (fr) * 2014-05-27 2016-05-13 Snecma Platine d'etancheite a fonction de fusible
US10648481B2 (en) 2014-11-17 2020-05-12 United Technologies Corporation Fiber reinforced spacer for a gas turbine engine
US10662793B2 (en) 2014-12-01 2020-05-26 General Electric Company Turbine wheel cover-plate mounted gas turbine interstage seal
US10337345B2 (en) 2015-02-20 2019-07-02 General Electric Company Bucket mounted multi-stage turbine interstage seal and method of assembly
US20170328203A1 (en) * 2016-05-10 2017-11-16 General Electric Company Turbine assembly, turbine inner wall assembly, and turbine assembly method
US10533445B2 (en) * 2016-08-23 2020-01-14 United Technologies Corporation Rim seal for gas turbine engine
FR3057300B1 (fr) 2016-10-07 2018-10-05 Safran Aircraft Engines Assemblage d'anneau mobile de turbine de turbomachine
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IT202000004585A1 (it) * 2020-03-04 2021-09-04 Nuovo Pignone Tecnologie Srl Turbina e pala perfezionate per la protezione della radice dai gas caldi del percorso del flusso.

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US8376697B2 (en) * 2008-09-25 2013-02-19 Siemens Energy, Inc. Gas turbine sealing apparatus
US20100074731A1 (en) * 2008-09-25 2010-03-25 Wiebe David J Gas Turbine Sealing Apparatus
US20120003079A1 (en) * 2010-07-02 2012-01-05 General Electric Company Apparatus and system for sealing a turbine rotor
US8845284B2 (en) * 2010-07-02 2014-09-30 General Electric Company Apparatus and system for sealing a turbine rotor
US8864453B2 (en) 2012-01-20 2014-10-21 General Electric Company Near flow path seal for a turbomachine
US11459157B2 (en) 2012-02-13 2022-10-04 Polytex Fibers Llc Woven plastic bags with features that reduce leakage, breakage and infestations
US12234076B2 (en) 2012-02-13 2025-02-25 Polytex Fibers Llc Peelable easy open plastic bags
US10138751B2 (en) 2012-12-19 2018-11-27 United Technologies Corporation Segmented seal for a gas turbine engine
US10704468B2 (en) 2013-02-28 2020-07-07 Raytheon Technologies Corporation Method and apparatus for handling pre-diffuser airflow for cooling high pressure turbine components
US9957895B2 (en) 2013-02-28 2018-05-01 United Technologies Corporation Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers
US10337406B2 (en) 2013-02-28 2019-07-02 United Technologies Corporation Method and apparatus for handling pre-diffuser flow for cooling high pressure turbine components
US10669938B2 (en) 2013-02-28 2020-06-02 Raytheon Technologies Corporation Method and apparatus for selectively collecting pre-diffuser airflow
US10760491B2 (en) 2013-02-28 2020-09-01 Raytheon Technologies Corporation Method and apparatus for handling pre-diffuser airflow for use in adjusting a temperature profile
US10808616B2 (en) 2013-02-28 2020-10-20 Raytheon Technologies Corporation Method and apparatus for handling pre-diffuser airflow for cooling high pressure turbine components
US9605596B2 (en) 2013-03-08 2017-03-28 United Technologies Corporation Duct blocker seal assembly for a gas turbine engine
US10578026B2 (en) 2013-03-08 2020-03-03 United Technologies Corporation Duct blocker seal assembly for a gas turbine engine
US9441639B2 (en) * 2013-05-13 2016-09-13 General Electric Company Compressor rotor heat shield
US20140334929A1 (en) * 2013-05-13 2014-11-13 General Electric Company Compressor rotor heat shield
US20150110628A1 (en) * 2013-10-17 2015-04-23 Pratt & Whitney Canada Corp. Fastening system for rotor hubs
US10465519B2 (en) * 2013-10-17 2019-11-05 Pratt & Whitney Canada Corp. Fastening system for rotor hubs
US9404376B2 (en) 2013-10-28 2016-08-02 General Electric Company Sealing component for reducing secondary airflow in a turbine system
US12240675B2 (en) 2014-04-04 2025-03-04 Polytex Fibers Llc Woven plastic bags with angled and/or radial cuts
US11305927B2 (en) 2014-04-04 2022-04-19 Polytex Fibers Llc Easy open plastic bags
US12234075B2 (en) 2014-04-04 2025-02-25 Polytex Fibers Llc Woven plastic bags with features that reduce leakage, breakage, and infestations
US11801987B2 (en) 2014-04-04 2023-10-31 Polytex Fibers Llc Woven plastic bags with angled and/or radial cuts
US11472622B2 (en) 2014-04-04 2022-10-18 Polytex Fibers Llc Woven plastic bags with features that reduce leakage, breakage, and infestations
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US11339662B2 (en) * 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
US11111803B2 (en) 2019-06-05 2021-09-07 Doosan Heavy Industries & Construction Co., Ltd. Sealing structure between turbine rotor disk and interstage disk
KR102127429B1 (ko) 2019-06-05 2020-06-26 두산중공업 주식회사 터빈 로터 디스크와 인터스테이지 디스크 사이의 실링 구조

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JP5491874B2 (ja) 2014-05-14
EP2208860B1 (en) 2020-06-24
CN101845996A (zh) 2010-09-29
EP2208860A2 (en) 2010-07-21
JP2010164054A (ja) 2010-07-29

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